Thermally Perfect Augmentation of a Supersonic Inlet Design Tool That Uses Method of Characteristics
Available at: https://digitalcommons.calpoly.edu/theses/3086
Date of Award
6-2025
Degree Name
MS in Aerospace Engineering
Department/Program
Aerospace Engineering
College
College of Engineering
Advisor
David Marshall
Advisor Department
Aerospace Engineering
Advisor College
College of Engineering
Abstract
This work is the first in a series to augment a supersonic air inlet design tool based in Python 3 to incorporate new models that increase the range of applicability of the tool. This effort focuses on improving the thermodynamics model by incorporating a thermally perfect gas model. This tool utilizes method of characteristics to solve the governing equations for an inviscid, irrotational, isentropic, steady, supersonic flow field. Multiple test cases are used to assess the accuracy of all new models. A comparison is made between the original code’s test case for a supersonic inlet at low temperatures to verify the implementation. Another test with high temperatures is presented to demonstrate the new model’s effects on the flow field. Finally, a simple geometry for hypersonic flow is created and analyzed so later work can validate the models with experimental data.
Included in
Aerodynamics and Fluid Mechanics Commons, Aeronautical Vehicles Commons, Other Aerospace Engineering Commons, Propulsion and Power Commons